A bifurcated inlet scoop frame for a gas turbine engine and method of using such frame for a gas turbine engine are disclosed. The bifurcated inlet scoop frame having a nose, a first side panel, and a second side panel. The first side panel and the nose defining a first inlet port. The second side panel and the nose defining a second inlet port. The method including the steps of providing a bifurcated inlet scoop frame, splitting the fan air flow, and receiving fan air through the bifurcated inlet scoop frame.


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    Title :

    Bifurcated inlet scoop for gas turbine engine


    Contributors:

    Publication date :

    2019-08-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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